EASA AD No.: 201 5

- 0 082

TE. CAP.00110

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 201 5 - 0 082

Date: 11 May 2015

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation.
This AD is issued in accordance with E U 748/2012 , Part 21

. A.3B. In accordance with E U 1321/2014 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may ope rate an aircraft to which an AD applies, except in accordance with the requirements of that AD , unless otherwise specified by the Agency [ EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

### Design Approval Holder’s Name : AIRBUS Type/Model designation(s) : A330 and A340 aeroplanes

TCDS Number: EASA.A.004 , EASA A.015

F oreign AD: Not applicable Supersedure: None



### ATA 71 Power Plant
– A ft and F orward E ngine M ount B olts
– Torque Check / Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie) Applicability: Airbus A330

- 201, A330

- 202, A330

- 203, A330

- 223, A330

- 223F, A330

- 243, A330

- 243F, A330

- 301, A330

- 302, A330

- 303, A330

- 321, A330

- 322, A330

- 323, A330

- 341, A330

- 342 and A330

- 343 aeroplanes, and Airbus A340

- 541, A340

- 542, A340

- 642 and A340

- 643 aeroplanes, from ma nufacturer serial number (MSN) 0715 to MSN 1507 inclusive , and MSN 1509 , except aeroplanes on which all engines have been removed and/or replaced since Airbus date of manufacture

. Reason: In 2013, during a pre

- delivery test on an A330 aeroplane fitted with Pratt & Whitney (PW) PW4170 engine s , an issue with N1 vibrations level on ENG1 was identified. W hile performing an engine removal, one forward engine mount bolt was found improperly torqued. The investigation concluded this was d ue to a production line engine installation quality issue

. Further analysis showed that some aeroplanes , delivered between Jun e 2006 and Jan uary 2014 , may have had the rear ( AFT ) and forward ( FWD ) engine mount bolts improperly torqued

. This condition, if not detected and corrected, could ultimately lead to an in

- flight detachment of the engine from the aeroplane, possibly resulting in damage to the aeroplane and/or injury to person s on the ground. Prompted by these findings, Airbus issue d four Alert Operators Transmission s (AOT) A71L004

- 14 ( for A330 aeroplanes fitted P ratt & W h itney (PW) engines ), AOT A71L006

- 14 ( for A330 aeroplanes fitted with G eneral E lectric (GE) engines ), AOT A71L005

- 14 ( for A330 aeroplanes fitted with Rolls Royce (RR)EASA AD No.: 201 5

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TE. CAP.00110

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Trent 700 engines ) and AOT A71L008

- 14 ( for A340 aeroplanes fitted with RR Trent 500 engines ) to provide torque check instructions. For the reasons described above, this AD requires a one - time torque check of the FWD and AFT engine mount bolts and, depending on findings, re - torque of the affected bolt (s) and/or replacement of all four bolts and associated nuts.
Effective Date: 25 May 2015 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: For the purpose of this AD, an affected engine is an engine that has never been removed and/or replaced since Airbus date of manufacture. For A330 aeroplanes fitted with PW engines : (1) Within 2 000 f light h ours (FH) , or during accomplishment of Airbus S ervice Bulletin (SB) A330

- 71

- 3028 , whichever occurs first after the effective date of this AD , accomplish a torque check of FWD and AFT engine mount bolts on each affected engine, at the locations as specified in, and in accordance with the instructions of Airbus AOT A71L004

- 14 Revision 01

. (2) If, during the torque check as required by paragraph (1) of this AD, any discrepancy is detected, within the compliance time defined in Airbus AOT A71L004

- 14 Revision 01 , depending on aeroplane configuration and f light c ycles (FC) / FH accumulated by the aeroplane since aeroplane first flight , accomplish the applicable corrective actions (re

- torque of each affected bolt and/or replace ment of all four bolts and associated nuts ) in accordance with the instructions of Airbus AOT A71L004

- 14 Revision 01

. For A330 aeroplanes fitted with GE engines: (3) Within 2 000 FH after the effective date of this AD, accomplish a torque check of FWD and AFT engine mount bolts on each affected engine, at the locations as specified in, and in accordance with the instructions of Airbus AOT A71L006

- 14. (4) If, during the torque check as required by paragraph (3) of this AD, any discrepancy is detected, within the compliance time defined in Airbus AOT A71L006

- 14, depending on FC / FH accumulated by the aeroplane since a eroplane first flight , accomplish the applicable corrective actions (re

torque of each affected bolt and/or replacement of all bolts and asso ciated nuts) in accordance with the instructions of Airbus AOT A71L00 6

- 14. For A330 aeroplanes fitted with RR Trent 700 engines: (5) Within 2 000 FH after the effective date of this AD, accomplish a torque check of FWD and AFT engine mount bolts on each affected engine, at the locations as specified in, and in accordance with the instructions of Airbus AOT A71L005

- 14 Revision 01

. (6) If, during the torque check as required by paragraph (5) of this AD, any discrepancy is detected, within the compliance tim e defined in Airbus AOT A71L005

- 14 Revision 01 , accomplish the applicable corrective actions (re

torque of each affected bolt and/or replacement of all four bolts and associated nuts/washers) in accordance with the instructions of Airbus AOT A71L005

- 14 Revision 01

. For A340 aeroplanes fitted with RR Trent 500 engines: (7) Within 2 000 FH after the effective date of this AD, accomplish a torque check of FWD and AFT engine mount bolts on each affected engine, at the locations as specified in, and in accordance with the instructions of Airbus AOT A71L008

- 14 Revision 01

. (8) If, during the torque check as required by paragraph (7) of this AD, any discrepancy is detected, within the compliance time defined in Airbus AOTEASA AD No.: 201 5

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TE. CAP.00110

- 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. A71L008

- 14 Revision 01 , accomplish the applicable corrective actions (re

torque of each affected bolt and/or replacement of all four bolts and associated nuts/washers) in accordance with the instructions of Airbus AOT A71L008

- 14 Revision 01

. For all A330 aeroplanes and A340 - 500/ - 600 aeroplanes: (9 ) A t orque check of all FWD and AFT engine mount bolts o f each affected engine on an aeroplane , accomplished before the effective date of this AD , in accordance with the instructions of Airbus AOT A71L004

- 14 or AOT A71L005

- 14 or A71L008

- 14 at original issue , as applicable, is an acceptable method to comply with the requirements of paragraph s (1), (5) and (7) of this AD , as applicable, for that aeroplane, provided that no discrepancy was detected during the torque check. ( 10 ) Within 30 days after the torque check as required by this AD, or within 30 days after the effective date of this AD, whichever occurs later , report the results of this check (including no discrepancies) to Airbus.
Ref. Public ations: Airbus AOT A71L004

- 14 dated 01 April 2014 , or Revision 01 dated 07 April 2014

. Airbus AOT A71L006

- 14 dated 22 July 2014. Airbus AOT A71L005

- 14 dated 29 September 2014 , or Revision 01 dated 11 December 2014

. Airbus AOT A71L008

- 14 dated 29 September 2014 , or Revision 01 dated 18 December 2014

. The u se of later approved revisions of the s e document s is acceptable for compliance with the requirements of this AD.
Remarks: 1. If requested and appropriately substantiated , EASA can approve Alternative Methods of Compliance for this AD. 2. Based on t he required actions and the compliance time, EASA have decided to issue a Final AD with Request for Comments , postponing the public consultation process until after publication

. 3. Enquiries regarding this A D should be referred to the Safety Information Section, Certification Directorate , EASA. E

- mail : ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirements in this AD, please contact: Airbus

– Airworthiness Office

– EIAL; E

- mail: airworthiness.A330

- A340@airbus.com

.